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Full-Scale Wind-Tunnel Tests of a PCA-2 Autogiro RotorThis report presents the results of force tests on and air-flow surveys near PCA-2 autogiro rotor in the NACA full-scale wind tunnel. The force tests were made at three pitch settings and several rotor speeds; the effect of fairing protuberances on the rotor blade was determined. Induced downwash and yaw angles were determined at low tip-speed ratios in a plane 1 1/2 feet above the path of the blade tips. The results show that the maximum l/d of the rotor cannot be appreciably increased by increasing the blade pitch angle above about 4.5 degrees at the blade tip; that the protuberances on the blades cause more than 5 percent of the total rotor drag; and that the rotor center-of-pressure travel is very small.
Document ID
19930091587
Document Type
Other
Authors
Wheatley, John B
Hood, Manley J
Date Acquired
September 6, 2013
Publication Date
January 1, 1935
Report/Patent Number
NACA-TR-515
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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